JPS63255528A - Fuel injector assembly for gas turbine - Google Patents

Fuel injector assembly for gas turbine

Info

Publication number
JPS63255528A
JPS63255528A JP63082117A JP8211788A JPS63255528A JP S63255528 A JPS63255528 A JP S63255528A JP 63082117 A JP63082117 A JP 63082117A JP 8211788 A JP8211788 A JP 8211788A JP S63255528 A JPS63255528 A JP S63255528A
Authority
JP
Japan
Prior art keywords
air
fuel
fuel injector
fuel injection
gas turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
JP63082117A
Other languages
Japanese (ja)
Other versions
JP2866960B2 (en
Inventor
リチャード・ダブリュ・ライト
フランシス・シー・ペイン・ジュニア
ジョン・エイ・マシューズ
エドマンド・イー・ストリーベル
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of JPS63255528A publication Critical patent/JPS63255528A/en
Application granted granted Critical
Publication of JP2866960B2 publication Critical patent/JP2866960B2/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • F23D11/107—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet at least one of both being subjected to a swirling motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

【発明の詳細な説明】 産業上の利用分野 本発明はガスタービンの燃焼室内へ燃料を噴霧するため
の噴射装置に係り、特に空気プラスト型ノズル組立体の
安定性の改良に係る。DETAILED DESCRIPTION OF THE INVENTION Field of the Invention The present invention relates to an injection device for atomizing fuel into a combustion chamber of a gas turbine, and more particularly to improving the stability of air-plast type nozzle assemblies.

従来の技術 ガスタービンの燃焼室は従来、乱れ騒ぐ高速ガスの容積
を郭定する金属製外殻又はライナーを有しており、その
内部にて燃焼が行なわれる。再循環領域が形成されるこ
とは最も重要であり、それは、実質的な速度を、燃焼が
行なわれるに適した速度まで、若しくはそれを下回るま
でに低下させる。この安定領域は、燃焼室全体のための
点火源即ち種火の源発地を準備する。BACKGROUND OF THE INVENTION Gas turbine combustion chambers traditionally have a metal shell or liner that defines a volume of turbulent high-velocity gases within which combustion takes place. Most importantly, a recirculation zone is created, which reduces the net velocity to or below a velocity suitable for combustion to take place. This stable region provides a source of ignition or pilot flame for the entire combustion chamber.

空気ブラスト型噴射装置は従来、円錐形の燃料噴霧パタ
ーンを用いており、その円錐の内側には、燃焼支持空気
の一部としての内側空気の供給が行なわれる。もう一つ
の燃焼支持空気を供給し且攪乱を誘発するため、円錐形
の噴霧と相互に作用しつつ渦を巻くようにして、もう一
つの空気が導入される。更にもう一つの空気が一層外側
の位置に導入され、この空気もまた一般に円錐形噴霧の
接線方向に誘導される。この空気流は付加的な燃焼支持
空気を供給するのみでなく、円錐形噴霧の外側の、炎の
安定性維持に役立つ再循環領域を生じさせる。Air blast injectors traditionally use a conical fuel spray pattern with a supply of internal air as part of the combustion support air inside the cone. Additional air is introduced in a swirling manner interacting with the conical spray to provide additional combustion support air and induce disturbance. Further air is introduced at a further outer location, and this air is also directed generally tangentially to the spray cone. This airflow not only provides additional combustion support air, but also creates a recirculation area outside the spray cone that helps maintain flame stability.

発明が解決しようとする課題 しかしながら我々は、再循環領域は生ずるけれどもこの
領域内には極めてわずかな燃料しか導入されないので、
この再循環領域では空気が優勢であることを知った。Problem to be Solved by the Invention However, we have found that although a recirculation region occurs, very little fuel is introduced into this region.
We learned that air predominates in this recirculation region.

発明の概要 空気ブラスト型燃料噴射装置は、略中空な円錐形をした
燃料噴霧と、燃料噴射装置の軸に対し特徴的に同心の空
気供給とを有する。空気を誘導するための複数の互に分
離した空気ノズルは、燃料噴射装置の軸へと向けて真っ
すぐに狙いを定められている。これらのノズルは、燃料
ノズルの軸に平行な線から１２°乃至２５°の角度に位
置決めされている。それらは、配置された円周領域の６
０％以下を占めている互に分離したノズルであり、軸か
ら２５．４＋ｎｍ以内に配置されるのが望ましい。SUMMARY OF THE INVENTION An air blast fuel injector has a generally hollow cone-shaped fuel spray and an air supply characteristically concentric with the axis of the fuel injector. A plurality of separate air nozzles for directing air are aimed straight toward the axis of the fuel injector. These nozzles are positioned at an angle of 12° to 25° from a line parallel to the axis of the fuel nozzle. They are located at 6 of the circumferential area
Separate nozzles occupying less than 0% of the total diameter, preferably located within 25.4+nm from the axis.

このように配置した空気ノズルは、円錐を貫通して再循
環領域を破壊することは無いけれども相・当な量の燃料
を再循環領域内へ導入するに十分な透過力を有する。Air nozzles so arranged have sufficient penetration power to introduce a significant amount of fuel into the recirculation area without penetrating the cone and destroying the recirculation area.

実施例 第１図の全体的構成には、空気流を閉込めている高圧空
間１２を取囲むケーシング１０が図示されている。この
ケーシング内には燃焼室ライナ１４と、該燃焼室ライナ
内に配置されるべく支柱１８に据付けられた燃料噴射装
置１６とがある。燃料は供給路２０を通過し、燃料噴射
装置１６の出口にて環状空間を通って噴出する。斜行通
路２２によって燃料はわずかに渦を巻き、それにより、
燃料噴射装置１６の円周の周りに均等に燃料が配分され
る。DESCRIPTION OF THE PREFERRED EMBODIMENTS The general arrangement of FIG. 1 shows a casing 10 surrounding a high pressure space 12 confining the air flow. Within the casing is a combustion chamber liner 14 and a fuel injector 16 mounted on a strut 18 to be disposed within the combustion chamber liner. The fuel passes through the supply channel 20 and is injected through the annular space at the outlet of the fuel injector 16 . The fuel is slightly swirled by the diagonal passage 22, so that
The fuel is evenly distributed around the circumference of the fuel injector 16.

内側空気流２４は燃料噴射装置の内側を通っており、若
し必要ならば渦形成具２６により渦を形成されてよい。The inner airflow 24 passes inside the fuel injector and may be vortexed by a vortex former 26 if desired.

燃焼室ライナ１４は開口部を有しており、燃焼室ライナ
と隔壁３０との間にもう一つの高圧空間２８を形成する
。外側空気３２は、高圧空間２８から燃焼室３６の中へ
と渦形成具３４を通過する。内側空気２４と外側空気３
２と燃料との相互作用は、燃焼室内への、６０°乃至７
０°の開先角度を有する燃料と空気との中空な円錐形の
噴出をもたらす。Combustion chamber liner 14 has an opening to define another high pressure space 28 between the combustion chamber liner and bulkhead 30 . External air 32 passes from high pressure space 28 into combustion chamber 36 through vortex former 34 . Inner air 24 and outer air 3
The interaction between 2 and the fuel is between 60° and 7° into the combustion chamber.
Provides a hollow cone-shaped jet of fuel and air with an included angle of 0°.

滑動ガイドプレート３８が隔壁３０に対して燃料噴射装
置を支持し、それにより、燃焼室ライナ１４の支持部材
と支柱１８との間の相対的移動を伴なう膨張を許容する
。もう一つの空気流４０が、互に分離した空気ノズル４
２により前記ガイドプレートを通過する。A sliding guide plate 38 supports the fuel injector against the bulkhead 30, thereby allowing expansion with relative movement between the support member of the combustion chamber liner 14 and the strut 18. Another air flow 40 flows through air nozzles 4 separated from each other.
2 to pass through the guide plate.

分離したノズルの詳細は、第２図と第３図と第４図とに
一層明確に示されている。直径４０．６４ｍｍの円４４
の上に各々直径２．６６７ｍｍのノズル４２が２４個配
置されているので、ノズル４２の開口の合計は、円４４
の円周の略５０％にのぼることが判る。こうして、互に
分離した多数の空気ジェットが、燃焼室内の円錐形流出
パターンへと向けてノズル４２を通過する。Details of the separate nozzles are shown more clearly in FIGS. 2, 3 and 4. Circle 44 with a diameter of 40.64 mm
Since 24 nozzles 42 each having a diameter of 2.667 mm are arranged on the top, the total opening of the nozzles 42 is a circle 44.
It can be seen that it accounts for approximately 50% of the circumference of . Thus, a number of separated air jets pass through the nozzle 42 into a conical exit pattern within the combustion chamber.

これらのノズルは燃料噴射装置の中心軸４６へと向けて
真っすぐに狙いを定められており、また、符号４７にて
第４図に示されている如く、中心軸４６に平行な線４８
に対し１５°の角度を成すようにしてこれらのノズルは
狙いを定められている。These nozzles are aimed straight toward the central axis 46 of the fuel injector, and are aligned with a line 48 parallel to the central axis 46, as shown in FIG. 4 at 47.
These nozzles are aimed at an angle of 15° to

内側空気流２４と外側空気流３２との和は、燃焼器へ送
る空気流の総計の約７％に達する。もう一つの、付加的
空気流４０は、空気流の総計の２％乃至４％にあたる。The sum of inner airflow 24 and outer airflow 32 amounts to about 7% of the total airflow to the combustor. Another, additional airflow 40 represents 2% to 4% of the total airflow.

付加的空気流４０が内側空気流と外側空気流との和の２
５％乃至６０％の間にあるこの条件が、燃料を含んだ安
定的再循環領域を生ずるに十分な相対的な運動量を与え
る。The additional air flow 40 is equal to 2 of the inner air flow plus the outer air flow.
This condition of between 5% and 60% provides sufficient relative momentum to create a stable recirculation region containing fuel.

空気流４０は、主たる燃焼用流出パターン５０と相互作
用をして、再循環領域５２を形成する。Airflow 40 interacts with the main combustion exit pattern 50 to form a recirculation region 52 .

従来の技術の教えるところによれば、符号４０にて示さ
れたものと類似の、円錐形パターン５０へと向けられる
空気は既に導入されているけれども、それは一般に前記
パターンの接線方向へと指向させられている。こうした
空気は幾らかの再循環領域を作り出すけれども、この領
域は、稀薄な燃料しか含まないことが知られている。そ
の上、燃料噴射ノズルの中心軸４６へと向けて空気４０
を導入されてすらも、その燃料噴射装置の中心軸に平行
な線に対して１２°を下回るような角度をもってしては
不十分な再循環しか得られないことを我々は見出した。The prior art teaches that although air has already been introduced which is directed into a conical pattern 50, similar to that shown at 40, it is generally directed tangentially to said pattern. It is being Although such air creates some recirculation area, this area is known to contain only lean fuel. Additionally, air 40 is directed toward the central axis 46 of the fuel injection nozzle.
We have found that, even when introduced, insufficient recirculation is obtained with angles less than 12 degrees relative to a line parallel to the central axis of the fuel injector.

他方、燃料噴射装置に対する角度が余りに急勾配になれ
ば、この空気流は円錐を貫通してしまうので効果的な再
循環領域を生成することは出来ないことが判った。従っ
て、中心軸に平行な線から１２°乃至２５°の角度をも
ってノズル４２を真っすぐに中心軸４６へと向けて配置
することにより、十分な量の燃料を再循環領域５２へ導
入するに適切な円錐５０透過力を得られることが判った
。これは、従来技術のシステムによっては達成されるこ
との無かった運転の安定性を実現する。On the other hand, it has been found that if the angle to the fuel injector is too steep, this air flow will pass through the cone and no effective recirculation area can be created. Accordingly, by orienting the nozzle 42 straight toward the central axis 46 at an angle of 12° to 25° from a line parallel to the central axis, a suitable amount of fuel can be introduced into the recirculation region 52. It was found that a cone 50 penetration power could be obtained. This provides operational stability not achieved by prior art systems.

【図面の簡単な説明】[Brief explanation of the drawing]

第１図は、本発明の一実施例である燃料噴射装置組立体
の全体的構成図である。 第２図は、囲繞空気ノズルを伴うガイドリングの詳細図
である。 第３図は、第２図の一部分の断面図であり、中心軸に一
致するようにして配置されたノズルの配置方向を示す。 第４図は、ガイドプレートの断面図であり、中心軸へと
向かうノズルの配置方向を示す。 １０・・・ケーシング、１２・・・高圧空間、１４・・
・燃焼室ライナ、１６・・・燃料噴射装置、１８・・・
支柱。 ２０・・・供給路、２２・・・斜行通路、２４・・・内
側空気流、２６・・・渦形成翼、２８・・・第二の高圧
空間、３０・・・隔壁、３２・・・外側空気流、３４・
・・渦形成翼。 ３６・・・燃焼室、３８・・・滑動ガイドプレート、４
０・・・付加的空気流、４２・・・ノズル、４４・・・
ノズルが配置された円、４６・・・中心軸、４７・・・
ノズルが指向する方向、４８・・・中心軸に平行な線、
５０・・・主たる燃焼用流出パターン、５２・・・再循
環領域特許出願人　　ユナイテッド・チクノロシーズ・
コーポレイション　　譬FIG. 1 is an overall configuration diagram of a fuel injection device assembly according to an embodiment of the present invention. FIG. 2 is a detailed view of the guide ring with surrounding air nozzle. FIG. 3 is a cross-sectional view of a portion of FIG. 2, showing the direction in which the nozzles are arranged to coincide with the central axis. FIG. 4 is a cross-sectional view of the guide plate, showing the nozzle arrangement direction toward the central axis. 10...Casing, 12...High pressure space, 14...
・Combustion chamber liner, 16...Fuel injection device, 18...
Prop. 20... Supply path, 22... Diagonal passage, 24... Inner air flow, 26... Vortex forming blade, 28... Second high pressure space, 30... Partition wall, 32...・Outside airflow, 34・
... Vortex forming wing. 36... Combustion chamber, 38... Sliding guide plate, 4
0... Additional air flow, 42... Nozzle, 44...
Circle where nozzles are arranged, 46... Central axis, 47...
The direction in which the nozzle is oriented, 48... A line parallel to the central axis,
50...Primary combustion outflow pattern, 52...Recirculation area Patent applicant United Chiknoroses
corporation parable

Claims (1)

【特許請求の範囲】 燃料噴射装置の軸と同心にして略中空な円錘状の燃料と
空気との噴霧を射出するための燃料噴射手段と、 前記中空円錘状噴霧内の中心に内側空気を誘導する手段
と、 ほぼ前記中空円錘状噴霧の接線方向へと前記円錘形状の
外側へ外側空気を誘導する手段と、前記燃料噴射手段と
前記の外側空気誘導手段とを取囲んでおり且前記燃料噴
射手段の軸へと向けて真っすぐにもう一つの空気を指向
させている複数の互に分離した囲繞空気ノズルとを含む
ガスタービン燃焼器用燃料噴射装置組立体。[Scope of Claims] A fuel injection means for injecting a substantially hollow conical fuel and air spray concentrically with the axis of the fuel injection device, and an inner air at the center of the hollow conical spray. means for guiding outer air to the outside of the conical shape substantially in a tangential direction to the hollow conical spray; and surrounding the fuel injection means and the outer air guiding means. and a plurality of discrete surrounding air nozzles directing another air directly toward an axis of the fuel injection means.
JP63082117A 1987-04-06 1988-04-01 Gas turbine fuel injector assembly Expired - Fee Related JP2866960B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US07/034,366 US4773596A (en) 1987-04-06 1987-04-06 Airblast fuel injector
US034,366 1987-04-06

Publications (2)

Publication Number Publication Date
JPS63255528A true JPS63255528A (en) 1988-10-21
JP2866960B2 JP2866960B2 (en) 1999-03-08

Family

ID=21875973

Family Applications (1)

Application Number Title Priority Date Filing Date
JP63082117A Expired - Fee Related JP2866960B2 (en) 1987-04-06 1988-04-01 Gas turbine fuel injector assembly

Country Status (5)

Country Link
US (1) US4773596A (en)
EP (1) EP0286569B1 (en)
JP (1) JP2866960B2 (en)
CA (1) CA1280611C (en)
DE (1) DE3860542D1 (en)

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JPH11257665A (en) * 1997-12-31 1999-09-21 United Technol Corp <Utc> Low nox combustor for gas turbine engine
JP2000074373A (en) * 1998-09-01 2000-03-14 Honda Motor Co Ltd Combustor for gas turbine engine

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US5288021A (en) * 1992-08-03 1994-02-22 Solar Turbines Incorporated Injection nozzle tip cooling
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IL106616A (en) * 1993-08-08 1997-06-10 Elhanan Tavor Atomizer
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US5467926A (en) * 1994-02-10 1995-11-21 Solar Turbines Incorporated Injector having low tip temperature
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Also Published As

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EP0286569A2 (en) 1988-10-12
EP0286569A3 (en) 1989-03-01
DE3860542D1 (en) 1990-10-11
US4773596A (en) 1988-09-27
CA1280611C (en) 1991-02-26
EP0286569B1 (en) 1990-09-05
JP2866960B2 (en) 1999-03-08

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